US4907946A - Resiliently mounted outlet guide vane - Google Patents

Resiliently mounted outlet guide vane Download PDF

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Publication number
US4907946A
US4907946A US07/230,392 US23039288A US4907946A US 4907946 A US4907946 A US 4907946A US 23039288 A US23039288 A US 23039288A US 4907946 A US4907946 A US 4907946A
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US
United States
Prior art keywords
outlet guide
guide vanes
mounting assembly
support members
socket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US07/230,392
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English (en)
Inventor
John J. Ciokajlo
Daniel S. Vogt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US07/230,392 priority Critical patent/US4907946A/en
Assigned to GENERAL ELECTRIC COMPANY, A NY CORP. reassignment GENERAL ELECTRIC COMPANY, A NY CORP. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: CIOKAJLO, JOHN J., VOGT, DANIEL S.
Priority to FR8910101A priority patent/FR2635358B1/fr
Priority to DE3925443A priority patent/DE3925443C2/de
Priority to JP1201530A priority patent/JP2845965B2/ja
Priority to IT8921465A priority patent/IT1230537B/it
Priority to GB8918196A priority patent/GB2221725B/en
Application granted granted Critical
Publication of US4907946A publication Critical patent/US4907946A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention concerns a mounting assembly adaptable for use with either ceramic or metallic outlet guide vane airfoils and particularly relates to a cantilevered, spring loaded mounting assembly which may be preloaded to maintain a compressive force on the airfoils throughout all phases of engine operation and shut down.
  • the outlet guide vanes are usually arranged between inner and outer engine frame members such as the inner and outer casings.
  • the airfoil profile of the outlet guide vanes channels the whirling vertical gasses into a plurality of evenly flowing axial streams which are conducive to optimum afterburner performance.
  • the even axial flow aids in controlling the diffusion of the exiting fluid through the afterburner thereby promoting the full combustion of all oxygen present in the exhaust gasses.
  • the present invention has been developed to solve the problems noted above and therefore has as a primary object the provision of a resilient mounting assembly for turbine engine outlet guide vanes.
  • the mounting assembly incorporates cantilevered beams for applying a compressive force on each outlet guide vane throughout engine operation and shut down.
  • Another object is to provide an outlet guide vane mounting assembly which allows the outlet guide vanes to thermally expand and contract without excessive constraint so as to minimize thermal stresses within the outlet guide vanes and thereby increase their useful life.
  • a further object is to provide an outlet guide vane mounting assembly constructed of economical lightweight castings for reducing costs and facilitating assembly by avoiding the use of time consuming welding and riveting operations.
  • Yet another object is to provide an outlet guide vane mounting assembly which is adapted for use with both metal and ceramic outlet guide vanes and which facilitates the interchange of ceramic outlet guide vanes with metal outlet guide vanes.
  • Still another object of the invention is the provision of an outlet guide vane assembly which facilitates the replacement and/or repair of individual outlet guide vanes.
  • the present invention includes an annular one piece cast inner support ring mounted concentrically within an annular one piece cast outer support ring. At least one of the support rings is formed with axially extending fingers or beams which serve as cantilevered spring members for resiliently clamping the outlet guide vanes between the support rings.
  • the outlet guide vanes are mounted separately from the turbine frame and therefore require strength only to support their aerodynamic deswirling loads. This arrangement allows for thinner outlet guide vanes which reduce aerodynamic blockage of the flowpath as compared to thicker and heavier outlet guide vanes which also serve as bearing and frame supports in conventional designs.
  • FIG. 1 is a schematic side elevation view, partially in section, of a gas turbine engine showing the general configuration of the gas turbine engine and the location of the turbine engine frame;
  • FIG. 2 is a side elevation view of the outlet guide vane mounting assembly connected to a turbine frame and showing the interchangeability between ceramic and metal outlet guide vanes;
  • FIG. 3 is an exploded perspective view, partly in section showing the details of the mounting assembly for ceramic outlet guide vanes;
  • FIG. 4 is a fragmental sectional view taken along line A--A of FIG. 2;
  • FIG. 5 is an enlarge fragmental side elevational view of the clamping members of FIG. 2;
  • FIG. 6 is a side elevation view of the outlet guide vane mounting assembly adapted for use with metal outlet guide vanes and connected to a turbine frame;
  • FIG. 7 is a schematic exploded partially sectioned view of the outlet guide vane assembly of FIG. 6.
  • FIG. 1 a portion of a gas turbine engine (10) is illustrated in partial cross-section.
  • the engine (10) includes an outer casing (12) which surrounds an annular flowpath (14) extending axially between an inlet (16) and an exhaust outlet (18) located at opposite ends of the engine (10).
  • ambient air is drawn into the inlet (16) and is compressed to a higher pressure in a compressor (20), from which the compressed air is discharged into an annular combustor (22) where fuel is burned to produce high energy products of combustion.
  • a compressor (20) From the combustor (22), the motive fluid is directed through a turbine (24) where a portion of its energy is extracted to drive the compressor (20), and the fluid is then discharged as a high energy stream through the exhaust outlet (18).
  • the engine (10) includes a front frame assembly (26) supporting a front bearing (28), a mid-frame assembly (30) supporting a mid-shaft bearing (32), and a turbine frame (34) supporting an aft bearing (36).
  • the rotor (38) is rotatably mounted in bearings (28, 32 and 36).
  • Each frame assembly (26, 30, and 34) respectively includes a plurality of radial support struts (40, 42, and 44) which project across the annular flowpath (14) to interconnect the inner and outer frame members of the frame assemblies. Since the temperature of the motive fluid flowing through the flowpath (14) changes very rapidly during transient engine operation, substantial thermal stresses can be created in the rigid frame assemblies if the struts are allowed to heat up and cool down at rates differing substantially from those of the inner and outer frame members. This is particularly true with respect to the turbine frame assembly (34) since the exhaust gases which surrounds the turbine frame assembly are subject to the most rapid and greatest changes in operating temperatures and resulting thermal stresses.
  • outlet guide vane mounting assembly of the present invention which minimizes such destructive thermal stresses, is illustrated in conjunction with a modified turbine frame assembly analagous to turbine frame (34).
  • the present invention is equally applicable to other rigid assemblies, which may also be exposed to motive fluid experiencing substantial and rapid changes in temperature.
  • the outlet guide vane mounting assembly is shown constructed from an annular 360° inner support member (46) aligned concentrically within an annular 360° outer support member (48). It is preferable to form both the inner and outer support members as one piece metal castings since castings can withstand up to 300° F. higher operating temperatures than corresponding parts fabricated from sheet metal, and in general, castings are more economical than welded or riveted fabrications. Moreover, with appropriate use of electrochemical discharge machining, castings can provide equivalent strength with lighter weight than similar welded or riveted parts. Of course, it is also possible to form the inner and outer support members as segmented or continuous machined rings.
  • the inner support member (46) may be attached to the turbine frame (34) along an annular flange (50) with removable threaded fasteners (52).
  • the inner support member (46) is preferably formed as a rigid shell to provide firm support to the easily removable and replaceable outlet guide vanes (54).
  • Each outlet guide vane (54) is preferably designed as an uncooled ceramic matrix composite vane which is firmly but resiliently clamped to the inner support member (46) under a compressive spring load provided by the outer support member (48).
  • thirty-six outlet guide vanes are evenly spaced in a spoked array between the inner and outer support members (46, 48) to eliminate the tangential or swirling component of the exiting gasses. As best seen in FIG.
  • the outer support member (48) is formed with mounting holes (56) which receive forward frame bolts (58) for attaching the outer support member (48) to the engine frame (34).
  • Forward bolts (56) along with aft bolts (60) are also arranged in a circumferential spoked array to provide a clamping force for clamping the annular outer casing (12) and inner frame ring (62) to radially extending spacer struts (64) positioned between the forward and aft bolts.
  • Ten or twelve spacer struts (64) have been found adequate to provide sufficient strength and rigidity to the engine frame (34), although any number of evenly distributed spacer struts may be used as long as adequate mechanical support is provided.
  • the threaded fasteners (52) which mount the inner support member (46) to the inner frame ring (62) also serve to fasten the inner support member (48) and inner frame ring (62) to an inner casing (66).
  • Inner casing (66) supports aft bearing (36) in a conventional fashion.
  • the mounting holes (56) are positioned so as to axially and radially locate the outer support member (48) with respect to the engine frame (34), and the forward bolts (58).
  • axial slots (70) and radial slots (72) reduce the rigidity of the outer support member (48) and form an annular series of axially extending cantilevered support beams (74) which radially and axially constrain the outlets guide vane boss (100).
  • Each support beam (74) has a radial dimension less than the combined radial dimension of the inner support member (46), vanes (54), and outer boss (100), thereby creating an interference fit and an initial compressive radial load between the support beams (74) and vane assembly (98, 54, and 96).
  • Support beams (74) act as spring members which deflect radially outwardly upon assembly so as to provide a radially inwardly directed compressive load upon the outlet guide vanes (54).
  • a variable but continuous compressive load is maintained upon the outlet guide vanes (54) throughout engine operation and shut down.
  • this spring loaded outlet guide vane mounting assembly is its ability to maintain intimate contact between the ceramic outlet guide vanes (54) and the metal support beams (74) throughout large and rapid changes in temperature, notwithstanding the large difference between their coefficients of thermal expansion.
  • the inner support member (46) and the outlet guide vane (54) are generally hotter than the outer support member (48). This results in the radially outward thermal growth of the inner support member (46) and the outlet guide vane into the cooler outer support member (48). This differential thermal growth results in the application of additional compressive force to the outlet guide vanes.
  • the outer support members (48) engage the outlet guide vanes (54) with a flexible and resilient spring biased contact, the total compressive force on the outlet guide vanes (54) can be easily controlled and limited to acceptable values through appropriate spring design of the support beams (74).
  • FIGS. 3, 4 and 5 Additional details of the mounting assembly adapted for ceramic outlet guide vanes are depicted in FIGS. 3, 4 and 5 wherein flanged metal sockets (76) are shown integrally formed around the circumference of the outer support member (48).
  • Each socket (76) is formed with a pair of opposed radially inwardly converging walls (78) which diverge axially forwardly to meet a radially extending mounting flange (80).
  • the sockets (76) including the walls (78) and flange (80) may be separately cost and welded to the beam supports (74) along weld lines (82).
  • a separate metal socket clamp (84) is formed with a pair of opposed, radially inwardly converging cantelevered walls (86) which diverge axially rearwardly to meet a radially extending mounting flange (88). Slots (90) (FIGS. 3 and 5) are formed between the walls (86) and roof (92) of the socket clamp (84) to allow the walls (86) to act as flexible spring loaded biasing members to secure and clamp the outlet guide vanes (54) to the outer support member (48), as discussed further below. Similar flanged sockets (94) and socket clamps (96) are provided on the inner support member (46) as seen in FIG. 2.
  • a vane foot support (98) is integrally cast from a ceramic matrix composite material for supporting the radially inner and outer ends of the outlet guide vanes (54) within the sockets (76, 94) and socket clamps (84, 96).
  • Each vane foot support (98) is formed with an elongated generally hexagonal boss (100) having axially projecting ridges (102).
  • An elongated pocket or channel (104) is formed within each boss (100) and axial ridge (102) for receiving a radial end portion (106) (FIG. 4) of each outlet guide vane (54) with a close fit.
  • each boss (100) generally matches the inner contours of the sockets (76, 94) and the socket clamps (84, 96). However, each boss (100) is dimensioned to form a wedged interference fit between the socket walls (78) and the cantelevered walls (86).
  • Each outlet guide vane (54) is fitted at opposed ends with a vane foot support (98) and positioned within the sockets (76, 94) on the inner and outer support members (46, 48).
  • a pair of socket clamps (84, 96) is then positioned over the exposed portions of the bosses (100) and secured to the inner and outer support members (46, 48) with threaded fasteners (108).
  • the threaded fasteners (108) (FIG. 3) pass through mounting holes (110) in the mounting flanges (80, 88) and as the threaded fasteners (108) are torqued down, the mounting flanges abut one another to resiliently secure the outlet guide vanes (54) within the sockets (76, 94) and socket clamps (84, 96).
  • the side faces (112) of the bosses (100) are wedged between the opposed socket walls (78) of the sockets (76, 94)and the opposed cantelevered walls (86) of the socket clamps (84, 96).
  • the cantelevered walls (86) are circumferentially deflected outwardly by the boss (100) during this wedging action so as to provide a resilient circumferential clamping force therebetween.
  • This clamping force or preloading of the cantelevered walls (86) ensures a continuous tight fit between the ceramic boss (100) and the metal sockets (76, 94) and socket clamps (84, 96) throughout engine operation. Even with the significant difference in thermal growth between these ceramic and metal members during thermal cycling of the turbine engine (10), the outlet guide vanes (54) are securely held in place between the inner and outer support members (46, 48) without being undesirably constrained and overstressed between rigid supports.
  • the resilient support provided by the cantelevered support beams (74) and the cantelevered walls (86) of the socket clamps (84, 96) controls and limits the amount of thermal stresses within the outlet guide vanes (54) within acceptable values.
  • a metal sealing plate (114) may be applied over abutting edges (116) of the vane foot supports (98), as seen in FIG. 4.
  • a circumferential mounting flange (118) may be formed on each sealing plate (114) and a mounting hole (120) may be formed through the mounting flange (118) to secure the sealing plate (114) to the inner and outer support members (46, 48).
  • the sealing plates (114) restrict the flow of hot gasses through the axial gaps (122) formed between the abutting edges (116) of the vane foot supports (98).
  • FIGS. 6 and 7 A modified and somewhat simplified embodiment of the outlet guide vane mounting assembly is shown in FIGS. 6 and 7.
  • This mounting assembly is designed for use with metal outlet guide vanes (122), and eliminates the use of sockets and socket clamps.
  • the outer support member (46) is formed with axial and radial slots (70, 72) to provide the necessary freedom for radial thermal expansion of the outlet guide vanes (122).
  • Radially extending mounting tabs (124) are provided on opposed ends of the outlet guide vanes (122) for registering with radially extending mounting flanges (126, 128) respectively formed on the inner and outer support members (46, 48). Threaded fasteners (13) passing through mounting holes (132) in the mounting tabs (124) and through the mounting flanges (126, 128) removably secure the outlet guide vanes to the inner and outer support members (46, 48).
  • outlet guide vanes (54, 122) in both embodiments are not used as structural members to strengthen the engine frame (34), and because these outlet guide vanes are not exposed to high thermal stresses, they may be fabricated with relatively thin cross sections. That is, if the outlet guide vanes (54, 122) were exposed to the high compressive thermal stresses produced by rigid support members, the sections of the outlet guide vanes would have to be increased to withstand such loads.
  • This capability of designing the outlet guide vanes with thin sections is most desirable from an aerodynamic viewpoint as thin sectioned outlet guide vanes avoid choking or blocking the flow of the exhaust gasses passing through the engine flowpath (14), and aid in the uniform diffusion of the exhaust gasses.
  • outlet guide vane mounting assemblies disclosed above can be economically manufactured and assembled.
  • the bolted interconnection of the inner and outer support members (46, 48) to the engine frame (34) facilitates the replacement or substitution of a ceramic outlet guide vane assembly for a metal outlet guide vane assembly.
  • the bolted mounting assembly of the outlet guide vanes (54, 122) to the inner and outer support members (46, 48) greatly facilitates the replacement or repair of individual outlet guide vanes.
  • the inner support member (46) may be provided with biasing spring members analogous to the support beams (74) formed on the outer support member (48) in addition to or in place or the support beams (74) provided on the outer support member.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US07/230,392 1988-08-10 1988-08-10 Resiliently mounted outlet guide vane Expired - Fee Related US4907946A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US07/230,392 US4907946A (en) 1988-08-10 1988-08-10 Resiliently mounted outlet guide vane
FR8910101A FR2635358B1 (fr) 1988-08-10 1989-07-26 Ailette de guidage de sortie au montage elastique
DE3925443A DE3925443C2 (de) 1988-08-10 1989-08-01 Befestigungsanordnung
JP1201530A JP2845965B2 (ja) 1988-08-10 1989-08-04 弾性装着出口案内ベーン
IT8921465A IT1230537B (it) 1988-08-10 1989-08-07 Diffusori montati in modo resiliente.
GB8918196A GB2221725B (en) 1988-08-10 1989-08-09 Gas turbine outlet guide vane mounting.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/230,392 US4907946A (en) 1988-08-10 1988-08-10 Resiliently mounted outlet guide vane

Publications (1)

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US4907946A true US4907946A (en) 1990-03-13

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US07/230,392 Expired - Fee Related US4907946A (en) 1988-08-10 1988-08-10 Resiliently mounted outlet guide vane

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US (1) US4907946A (it)
JP (1) JP2845965B2 (it)
DE (1) DE3925443C2 (it)
FR (1) FR2635358B1 (it)
GB (1) GB2221725B (it)
IT (1) IT1230537B (it)

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US5165850A (en) * 1991-07-15 1992-11-24 General Electric Company Compressor discharge flowpath
US5249921A (en) * 1991-12-23 1993-10-05 General Electric Company Compressor outlet guide vane support
US5320487A (en) * 1993-01-19 1994-06-14 General Electric Company Spring clip made of a directionally solidified material for use in a gas turbine engine
US5357744A (en) * 1992-06-09 1994-10-25 General Electric Company Segmented turbine flowpath assembly
US6000906A (en) * 1997-09-12 1999-12-14 Alliedsignal Inc. Ceramic airfoil
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US6547518B1 (en) 2001-04-06 2003-04-15 General Electric Company Low hoop stress turbine frame support
US6648597B1 (en) 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
US20040043889A1 (en) * 2002-05-31 2004-03-04 Siemens Westinghouse Power Corporation Strain tolerant aggregate material
US20050167878A1 (en) * 2004-01-29 2005-08-04 Siemens Westinghouse Power Corporation Method of manufacturing a hybrid structure
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US20080181766A1 (en) * 2005-01-18 2008-07-31 Siemens Westinghouse Power Corporation Ceramic matrix composite vane with chordwise stiffener
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US20100254804A1 (en) * 2009-04-03 2010-10-07 Rolls-Royce Plc Stator vane assembly
US20110041313A1 (en) * 2009-08-24 2011-02-24 James Allister W Joining Mechanism with Stem Tension and Interlocked Compression Ring
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US20130115076A1 (en) * 2011-11-09 2013-05-09 Richard Bouchard Strut mounting arrangement for gas turbine exhaust case
US20130115051A1 (en) * 2011-11-09 2013-05-09 Richard Bouchard Gas turbine exhaust case with acoustic panels
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US8801372B2 (en) 2006-08-10 2014-08-12 United Technologies Corporation Turbine shroud thermal distortion control
US20160069200A1 (en) * 2013-06-17 2016-03-10 United Technologies Corporation Turbine Vane With Platform Pad
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US9970317B2 (en) 2014-10-31 2018-05-15 Rolls-Royce North America Technologies Inc. Vane assembly for a gas turbine engine
US10202865B2 (en) 2012-10-23 2019-02-12 General Electric Company Unducted thrust producing system
US10563528B2 (en) * 2017-05-23 2020-02-18 Rolls-Royce North American Technologies Inc. Turbine vane with ceramic matrix composite airfoil
US11300003B2 (en) 2012-10-23 2022-04-12 General Electric Company Unducted thrust producing system
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US11492918B1 (en) 2021-09-03 2022-11-08 General Electric Company Gas turbine engine with third stream
US20230175407A1 (en) * 2021-12-03 2023-06-08 General Electric Company Dovetailed composite outlet guide vane assembly and method of assembling thereof
US11680530B1 (en) 2022-04-27 2023-06-20 General Electric Company Heat exchanger capacity for one or more heat exchangers associated with a power gearbox of a turbofan engine
US11834992B2 (en) 2022-04-27 2023-12-05 General Electric Company Heat exchanger capacity for one or more heat exchangers associated with an accessory gearbox of a turbofan engine
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Also Published As

Publication number Publication date
DE3925443A1 (de) 1990-02-15
GB2221725B (en) 1993-05-05
FR2635358A1 (fr) 1990-02-16
GB2221725A (en) 1990-02-14
GB8918196D0 (en) 1989-09-20
JP2845965B2 (ja) 1999-01-13
DE3925443C2 (de) 1999-03-25
IT1230537B (it) 1991-10-28
FR2635358B1 (fr) 1994-07-08
JPH02256801A (ja) 1990-10-17
IT8921465A0 (it) 1989-08-07

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